CN107678357A - A kind of SUAV power distribution and management circuit system - Google Patents
A kind of SUAV power distribution and management circuit system Download PDFInfo
- Publication number
- CN107678357A CN107678357A CN201711022473.1A CN201711022473A CN107678357A CN 107678357 A CN107678357 A CN 107678357A CN 201711022473 A CN201711022473 A CN 201711022473A CN 107678357 A CN107678357 A CN 107678357A
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- power supply
- electricity
- power
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- chip microcomputer
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0423—Input/output
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- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B2219/00—Program-control systems
- G05B2219/20—Pc systems
- G05B2219/25—Pc structure of the system
- G05B2219/25257—Microcontroller
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- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
The invention discloses a kind of SUAV power distribution and management circuit system, including：Single-chip microcomputer, switching circuit 1, switching circuit 2 and switching circuit 3；Single-chip microcomputer gathers generator commutation filtered voltage Vin+, whether enters DC/DC input voltages working range according to Vin+ to control enabling and disabling for DC/DC modules；Generator commutation filtered voltage Vin+ is converted to 28V through DC/DC modules, enters switching circuit 1 jointly with 6S lithium battery groups and outside 28V electricity, completes three kinds of power supply seamless switchings, output voltage is supplied respectively to fly control, steering wheel and link through DC/DC conversions again after switching；Single-chip microcomputer obtains taking off of flying that control issues and flag bit and gathers voltage Vin+ after rectifying and wave-filtering, it is determined that giving load power supply after whether the 28V electricity of DC/DC conversions switches over selection with outside 28V electricity into switching circuit 2；28V and outside 28V electricity enters the switching selection of switching circuit 3 and charged to 6S lithium battery groups jointly after DC/DC conversions.
Description
Technical field
The invention belongs to unmanned plane power distribution and administrative skill field, is related to a kind of SUAV power distribution and pipe
Manage circuit system.
Background technology
The main research of onboard electrical system for distribution and power management techniques, can possess it is dynamical supply,
The lifting of distribution and power-supply management system for unmanned plane overall performance is significant.At present, most of small-sized fixed-wings
Unmanned plane still uses single lithium polymer battery group power supply plan, and with the increase of endurance, battery pack can be weighed increasingly on machine,
Do not allow for small-sized fixed-wing unmanned plane, this just turns into the big factor for restricting unmanned plane endurance, and single
Be present the risk of air crash when battery goes wrong in battery powered, and just solved using the unmanned plane of minitype airborne generator
Problem above, can either solve the problems, such as that battery pack restricts unmanned plane endurance, also can be that unmanned plane during flying is protected safely plus double
Danger.Another problem, that is, the conjunction to various power supplys on machine are necessarily drawn in application of the minitype airborne generator on unmanned plane
Reason distribution, control and management, the present invention specially develop efficient aiming at the unmanned plane for being provided with small generator system
Stable power distribution and management circuit.
The content of the invention
(1) goal of the invention
The purpose of the present invention is：There is provided a kind of SUAV power distribution and management circuit system so that hair is installed
The SUAV of electric system can be automatically completed to electricity according to the power supply handling characteristics in each stage in each working stage
Distribution, control and the management in source.
(2) technical scheme
In order to solve the above-mentioned technical problem, the present invention provides a kind of SUAV power distribution and management circuit system,
It includes：Single-chip microcomputer, switching circuit 1, switching circuit 2 and switching circuit 3；
Single-chip microcomputer gathers generator commutation filtered voltage Vin+, is worked according to whether Vin+ enters DC/DC input voltages
Scope controls enabling and disabling for DC/DC modules；Generator commutation filtered voltage Vin+ is converted to 28V through DC/DC modules,
Enter switching circuit 1 jointly with 6S lithium battery groups and outside 28V electricity, the seamless switching work(of three kinds of power supplys is completed by switching circuit 1
Can, the voltage exported after switching is converted into different voltage through DC/DC again and powered to control, steering wheel and link is flown；
Single-chip microcomputer obtains taking off of flying that control issues and flag bit and gathers voltage Vin+ after rectifying and wave-filtering, according to the two conditions
Determine powered after whether the 28V electricity of DC/DC conversions switches over selection with outside 28V electricity into switching circuit 2 to load；
28V and outside 28V electricity charges after entering the switching selection of switching circuit 3 jointly to 6S lithium battery groups after DC/DC conversions.
Wherein, in addition to：LED state display module, generator powered indicator lamp, external electrical power supply instruction are set thereon
Lamp, battery-powered indicator lamp, charge status indicating light and load power supply indicator lamp.
Wherein, the outside 28V electricity power supply signal of the single-chip microcomputer collection, the power supply feedback signal of switching circuit 1, according to two letters
Number Determines be currently any power supply to system power supply, and light the indicator lamp for being currently at power supply state, extinguish
Remaining two kinds of power supply indicator.
Wherein, whether the load power supply signal state of the single-chip microcomputer collection load power supply output end, determine current load
In power supply state, and light/extinguish respective loads power supply indicator lamp.
Wherein, the charging voltage signal and the charging of 6S lithium battery groups feedback that the single-chip microcomputer collection switching circuit 3 exports
Status signal determines which kind of charged state is current battery be in, and light/extinguish charge status indicating light.
Wherein, the switching circuit 1 includes power field effect tube controller and power-type FET, power-type field-effect
28V electricity after the drain D sending and receiving motor conversion of pipe, grid G connect power field effect tube controller, and source S connects power supply output Vout, work(
Rate FET controller connects 28V electricity after 6S lithium battery groups power supply, outside 28V electricity and generator convert, and selection determines that output is electric
Source.
Wherein, in addition to：Three-phase alternating current rectifying and wave-filtering, DC/DC conversions and control circuit, use standard three phase rectifier module
By three-phase alternating current it is whole be pulsating direct current, then filtered capacitor filtering, the amplitude of pulsating direct current is controlled within 1V, then pass through
DC/DC is converted to 28VDC, and single-chip microcomputer sees whether reach unlocking condition by gathering aircraft current state and rectifying and wave-filtering voltage,
Then control DC/DC's to make/forbidden energy by light-coupled isolation.
Wherein, the voltage that the switching circuit 1 exports after switching through isolate DC/DC modules by voltage be respectively converted into 12V,
5V and 15V, 12V electricity are transformed to work the electricity consumption 3.3V, 15V of single-chip microcomputer through power MOS controls output and disconnected through DC/DC again.
(3) beneficial effect
SUAV power distribution that above-mentioned technical proposal is provided and management circuit system, used in being provided with generator
On the small-sized fixed-wing unmanned plane of system, according to the power supply handling characteristics in each stage in unmanned aerial vehicle test and flight course
It is automatically performed the distribution, control and management of power supply.
Brief description of the drawings
Fig. 1 is power distribution and management circuit system theory diagram in the embodiment of the present invention.
Fig. 2 is three power supply switch circuit theory diagrams in the embodiment of the present invention.
Fig. 3 is that rectifying and wave-filtering and DC/DC make forbidden energy control circuit theory diagram in the embodiment of the present invention.
Fig. 4 is secondary power supply distribution and control circuit theory diagram in the embodiment of the present invention.
Embodiment
To make the purpose of the present invention, content and advantage clearer, with reference to the accompanying drawings and examples, to the present invention's
Embodiment is described in further detail.
In order to solve to be provided with the SUAV of generator system distribution of each working stage to power supply, control and
Management, a kind of power distribution and management circuit system are designed, complete automatic distribution, control and the pipe of each working stage power supply
Reason.
As shown in figure 1, single-chip microcomputer gathers generator commutation filtered voltage Vin+, it is defeated according to whether Vin+ enters DC/DC
Enter voltage power supply scope to control enabling and disabling for DC/DC modules.Generator commutation filtered voltage Vin+ is through DC/DC modules
28V is converted to, enters power supply switch circuit 1 jointly with 6S lithium battery groups and outside 28V electricity, three kinds of electricity is completed by switching circuit 1
The seamless handover function in source, the voltage exported after switching are converted into different voltage through DC/DC again and supplied to control, steering wheel and link is flown
Electricity.
Under arbitrary operational state, there can only be a kind of power supply to be in power supply state.What the winged control of single-chip microcomputer acquisition issued takes off
Flag bit simultaneously gathers voltage Vin+ after rectifying and wave-filtering, the 28V electricity changed through DC/DC according to the two conditional decisions whether with outside
28V electricity is powered after switching over selection into switching circuit 2 to load.
28V and outside 28V electricity charges after entering the switching selection of switching circuit 3 jointly to 6S lithium battery groups after DC/DC conversions.
The outside 28V electricity power supply signal of single-chip microcomputer collection, the power supply feedback signal of switching circuit 1, according to the state of two signals
Decision is currently any power supply to system power supply, and lights the indicator lamp for being currently at power supply state, extinguishes remaining two kinds
Power supply indicator；Whether the load power supply signal state of single-chip microcomputer collection load power supply output end, determine current load in confession
Electricity condition, and light/extinguish respective loads power supply indicator lamp；Single-chip microcomputer collection switching circuit 3 export charging voltage signal and
The charging status signal of 6S lithium battery groups feedback determines which kind of charged state is current battery be in, and lights/extinguish charging
Status indicator lamp.
Accompanying drawing 2,3,4 is each subitem theory diagram.
Wherein Fig. 2 is three power supply switching principle block diagrams, namely the theory diagram of switching circuit 1.Switching circuit 1 includes power
FET controller and power-type FET, 28V electricity after the drain D sending and receiving motor conversion of power-type FET, grid G
Connect power field effect tube controller, source S meets power supply output Vout, power field effect tube controller connect 6S lithium battery groups power supply,
28V electricity after outside 28V electricity and generator conversion, selection determine out-put supply.
Fig. 3 is three-phase alternating current rectifying and wave-filtering, DC/DC conversions and control circuit, using standard three phase rectifier module by three-phase
It is pulsating direct current to exchange whole, then filtered capacitor filtering, and the amplitude of pulsating direct current is controlled within 1V, then is turned through DC/DC
28VDC is changed to, single-chip microcomputer is seen whether reach unlocking condition by gathering aircraft current state and rectifying and wave-filtering voltage, then passed through
Light-coupled isolation control DC/DC's makes/forbidden energy.
Fig. 4 is the theory diagram for supplying distribution after three kinds of power conversions to rear class airborne equipment, according to each equipment supply voltage
Difference, voltage is respectively converted into 12V, 5V and 15V by isolating DC/DC, 12V electricity is transformed to single-chip microcomputer through DC/DC again
Electricity consumption 3.3V, 15V work through power MOS controls output and disconnection.
Next to that distribution, control management method and the specific control logic of power distribution and management circuit to various power supplys,
28V power supplys, 6S battery powers and outside 28V power supplys carry out three power supplys after being filtered using LTC4414 chips to generator commutation
And two power supply switching；3 road voltage acquisition functions, 5 paths of LEDs state output indicator functions, generator are completed using single-chip microcomputer to supply
Electricity automatically turns on function, load power supply automatically turns on function.
The present embodiment system completes following functions.
1) three kinds of power supply handoff functionalities
Under arbitrary operational state, there can only be a kind of power supply to be in power supply state.
In unmanned aerial vehicle debugging mode, outside 28V power supplys are connected, whole avionics system is now supplied electricity to by outside 28V
Power supply, if ground debugging time is longer, it can so avoid using battery backup when ground is debugged, add winged
The crash time of machine；Remove outside 28V electricity, circuit can seamlessly switch to it is battery-powered, if rectification is filtered after engine start
Voltage >=30V and aircraft are not in takeoff condition after ripple, then circuit seamlessly switches to generator powered.
In flight course, if the filtered voltage >=30V of generator commutation and aircraft is not in takeoff condition, by
Generator powered, it can automatically switch in the case of remaining battery-powered.
Load only use outside 28V power supplys and generator commutation filter after 28V power supplys power, in any case all without using
6S battery powers are powered.
2) 3 road voltage acquisition function
Voltage acquisition function is that the AD peripheral hardwares carried by single-chip microcomputer realize the collection to voltage.
The voltage acquisition table of table 1
3) 5 paths of LEDs state outputs indicate
System power supply source is judged by LTC4414 feedback signal POWER_Signal and dispatch from foreign news agency voltage acquisition signal.
If POWER_Signal signal output high level, illustrate the electromechanical power supply that generates electricity；If POWER_Signal signal output low levels, say
Bright is remaining power supply mode, while judges dispatch from foreign news agency EX_POWER again, if EX_POWER is present, explanation is dispatch from foreign news agency power supply, otherwise
It is that battery pack is being powered.By the magnitude of voltage at monitors load power supply final output end, to judge current load whether in power supply
State.
By judging that the voltage of battery pack the charging signals CHARGE_Signal provided and the output end that charges is current to judge
Charged state, and drive LED light indicate different colours.If charging voltage is present, and CHARGE_Signal exports low electricity
It is flat, then it represents that battery is fully charged；If charging voltage is present, and CHARGE_Signal output high level, then it represents that charges；
If charging voltage is not present, no matter CHARGE_Signal signals when what state, represent battery do not charge now, traffic lights
All extinguish.
4) generator powered automatically turns on
It is to make what forbidden energy was realized by the Enable Pins of 28V power modules that generator powered, which automatically turns on function, and single-chip microcomputer leads to
The rectified filtered voltage VIN+ of collection engine in real time and takeoff condition flag bit are crossed to judge whether to reach system power supply
Unlocking condition, if meeting condition, single-chip microcomputer exports low level by PA8, enables power module.
The generator powered of table 2 opens logical table
5) load power supply automatically turns on：
Single-chip microcomputer judges whether to reach load power supply by gathering the rectified filtered voltage VIN+ of engine in real time
The condition of unlatching, such as reach unlocking condition, single-chip microcomputer exports low level by PA11 pins, opens load power supply.
Logical table is opened in the power supply of the load of table 3
| Input condition | Output |
| Voltage VIN+ after rectifying and wave-filtering | PA11 |
| ≥41V | 0 (load power supply) |
| ＜ 41V | 1 (load power-off) |
Effect of the present invention is unmanned plane using this power distribution and manages circuit, realizes each work rank in unmanned plane
Automatic distribution, control and the management of section power supply.
The small-sized long endurance unmanned aircraft of certain model, using this power distribution and management circuit, solve onboard generators power supply,
Three kinds of power supply switchings, battery pack charges online and automatic distribution, control and the problem of management of power supply.Circuit runs efficient stable,
So that the endurance and system reliability of certain model unmanned plane greatly promote.
Described above is only the preferred embodiment of the present invention, it is noted that for the ordinary skill people of the art
For member, without departing from the technical principles of the invention, some improvement and deformation can also be made, these are improved and deformation
Also it should be regarded as protection scope of the present invention.
Claims (8)
1. a kind of SUAV power distribution and management circuit system, it is characterised in that including：Single-chip microcomputer, switching circuit 1,
Switching circuit 2 and switching circuit 3；
Single-chip microcomputer gathers generator commutation filtered voltage Vin+, whether enters DC/DC input voltage working ranges according to Vin+
To control enabling and disabling for DC/DC modules；Generator commutation filtered voltage Vin+ is converted to 28V through DC/DC modules, with 6S
Lithium battery group and outside 28V electricity enter switching circuit 1 jointly, and the seamless handover function of three kinds of power supplys is completed by switching circuit 1, is cut
The voltage exported after changing is converted into different voltage through DC/DC again and powered to control, steering wheel and link is flown；
Single-chip microcomputer obtains taking off of flying that control issues and flag bit and gathers voltage Vin+ after rectifying and wave-filtering, according to the two conditional decisions
Powered after whether the 28V electricity of DC/DC conversions switches over selection with outside 28V electricity into switching circuit 2 to load；
28V and outside 28V electricity charges after entering the switching selection of switching circuit 3 jointly to 6S lithium battery groups after DC/DC conversions.
2. SUAV power distribution as claimed in claim 1 and management circuit system, it is characterised in that also include：LED
State display module, generator powered indicator lamp, external electrical power supply indicator lamp, battery-powered indicator lamp, charging are set thereon
Status indicator lamp and load power supply indicator lamp.
3. SUAV power distribution as claimed in claim 2 and management circuit system, it is characterised in that the single-chip microcomputer
Which the outside 28V electricity power supply signal of collection, the power supply feedback signal of switching circuit 1, be currently according to the Determines of two signals
Kind of power supply lights the indicator lamp for being currently at power supply state to system power supply, extinguishes remaining two kinds of power supply indicator.
4. SUAV power distribution as claimed in claim 3 and management circuit system, it is characterised in that the single-chip microcomputer
The load power supply signal state of load power supply output end is gathered, determines whether current load is in power supply state, and light/extinguish
Respective loads power supply indicator lamp.
5. SUAV power distribution as claimed in claim 4 and management circuit system, it is characterised in that the single-chip microcomputer
The charging voltage signal of the output of switching circuit 3 and the charging status signal of 6S lithium battery groups feedback are gathered to determine current battery
In which kind of charged state, and light/extinguish charge status indicating light.
6. SUAV power distribution as claimed in claim 1 and management circuit system, it is characterised in that the switching electricity
Road 1 includes power field effect tube controller and power-type FET, after the drain D sending and receiving motor conversion of power-type FET
28V electricity, grid G connect power field effect tube controller, and source S meets power supply output Vout, and power field effect tube controller connects 6S lithiums
28V electricity after battery power, outside 28V electricity and generator conversion, selection determine out-put supply.
7. SUAV power distribution as claimed in claim 1 and management circuit system, it is characterised in that also include：Three
Cross streams rectifying and wave-filtering, DC/DC conversions and control circuit are whole straight to pulse by three-phase alternating current using standard three phase rectifier module
Stream, then filtered capacitor filtering, the amplitude of pulsating direct current is controlled and is converted to 28VDC, monolithic within 1V, then through DC/DC
Machine sees whether reach unlocking condition by gathering aircraft current state and rectifying and wave-filtering voltage, is then controlled by light-coupled isolation
DC/DC's makes/forbidden energy.
8. SUAV power distribution as claimed in claim 1 and management circuit system, it is characterised in that the switching electricity
Voltage is respectively converted into 12V, 5V and 15V by the voltage that road 1 exports after switching through isolating DC/DC modules, and 12V electricity is again through DC/DC
Work the electricity consumption 3.3V, 15V of single-chip microcomputer are transformed to through power MOS controls output and is disconnected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711022473.1A CN107678357A (en) | 2017-10-27 | 2017-10-27 | A kind of SUAV power distribution and management circuit system |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711022473.1A CN107678357A (en) | 2017-10-27 | 2017-10-27 | A kind of SUAV power distribution and management circuit system |
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| Publication Number | Publication Date |
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| CN107678357A true CN107678357A (en) | 2018-02-09 |
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| CN201711022473.1A Pending CN107678357A (en) | 2017-10-27 | 2017-10-27 | A kind of SUAV power distribution and management circuit system |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110825150A (en) * | 2019-11-15 | 2020-02-21 | 彩虹无人机科技有限公司 | Unmanned aerial vehicle is with digital power supply unit who has distribution function |
| CN111959287A (en) * | 2020-08-28 | 2020-11-20 | 中国科学院工程热物理研究所 | Solar unmanned aerial vehicle and control method thereof, electronic device and medium |
| CN112193091A (en) * | 2020-12-07 | 2021-01-08 | 澄瑞电力科技（上海）有限公司 | Automatic power supply control system and method for electric ship |
| CN113364295A (en) * | 2020-03-06 | 2021-09-07 | 江苏和正特种装备有限公司 | High-efficient high-density airborne high-voltage power supply system |
| CN113553280A (en) * | 2021-06-21 | 2021-10-26 | 上海机电工程研究所 | Based on I2C bus integrated electronic platform multi-module time-sharing power-on method and system |
| CN113746159A (en) * | 2021-07-21 | 2021-12-03 | 河南牧原智能科技有限公司 | Robot and power management system thereof |
| CN114962007A (en) * | 2021-02-23 | 2022-08-30 | 昆明桑达科技有限公司 | Emergent starting circuit of unmanned aerial vehicle engine |
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| CN104659900A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Power supply system of unmanned helicopter |
| CN105471069A (en) * | 2016-01-05 | 2016-04-06 | 海鹰航空通用装备有限责任公司 | Vehicle-mounted power supply management and control system and equipment for small-sized unmanned aerial vehicle |
| CN105680554A (en) * | 2015-12-28 | 2016-06-15 | 海鹰航空通用装备有限责任公司 | Power supply and distribution control device for unmanned aerial vehicle |
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| CN104659900A (en) * | 2013-11-25 | 2015-05-27 | 中国直升机设计研究所 | Power supply system of unmanned helicopter |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110825150A (en) * | 2019-11-15 | 2020-02-21 | 彩虹无人机科技有限公司 | Unmanned aerial vehicle is with digital power supply unit who has distribution function |
| CN113364295A (en) * | 2020-03-06 | 2021-09-07 | 江苏和正特种装备有限公司 | High-efficient high-density airborne high-voltage power supply system |
| CN111959287A (en) * | 2020-08-28 | 2020-11-20 | 中国科学院工程热物理研究所 | Solar unmanned aerial vehicle and control method thereof, electronic device and medium |
| CN112193091A (en) * | 2020-12-07 | 2021-01-08 | 澄瑞电力科技（上海）有限公司 | Automatic power supply control system and method for electric ship |
| CN114962007A (en) * | 2021-02-23 | 2022-08-30 | 昆明桑达科技有限公司 | Emergent starting circuit of unmanned aerial vehicle engine |
| CN114962007B (en) * | 2021-02-23 | 2024-07-26 | 昆明桑达科技有限公司 | Unmanned aerial vehicle engine emergency starting circuit |
| CN113553280A (en) * | 2021-06-21 | 2021-10-26 | 上海机电工程研究所 | Based on I2C bus integrated electronic platform multi-module time-sharing power-on method and system |
| CN113746159A (en) * | 2021-07-21 | 2021-12-03 | 河南牧原智能科技有限公司 | Robot and power management system thereof |
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